Equation of motion for powered flight of particular stage of multistage vehicle is reduced to first-order linear differential equation in vehicle weight, whose coefficients are known functions of time, by assumption that trajectory is known; design parameters include total weight, payload weight, specific impulse, propellant mass fraction, and vehicle diameter; it is possible to include specified constraints on vehicle such as fineness ratio or burning rate of solid propellants; method for choosing best propellant and chamber pressure from given set of propellants, and example of determining optimum chamber pressure for sustainer stage of two-stage vehicle.


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    Titel :

    Rocket design for specified trajectory


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Adkins, C.N. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1965


    Format / Umfang :

    5 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Rocket design for a specified trajectory

    ADKINS, C. N. | AIAA | 1965


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    Rocket trajectory optimization

    Leitman, G. | Engineering Index Backfile | 1965


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    Trajectory Design of a Rocket-Scramjet-Rocket Multi-Stage Launch System

    Forbes-Spyratos, Sholto O. / Kearney, Michael P. / Smart, Michael K. et al. | AIAA | 2017